A large landing gear main wheel turning mechanism testing device and testing method

Abstract

The application provides a large landing gear main wheel turning mechanism testing device and a testing method, and belongs to the technical field of aircraft landing gear testing. The turning mechanism testing device comprises a support frame, a loading actuator, a cross beam, a turning loading mechanism, a wheel frame assembly and a test bed. The loading actuator is arranged on the support frame, one end of the loading actuator is connected with the cross beam, the other end of the loading actuator is connected with the support frame, and the loading actuator is used for adjusting the pressure of the wheel frame assembly on the test bed. The cross beam is pivotally connected with the support frame, one end of the cross beam is connected with the loading actuator, and the other end of the cross beam is provided with one or more wheel frame assemblies. The turning loading mechanism is arranged on the cross beam and used for applying a turning torque to the wheel frame assembly. The test bed is arranged on the support frame and used for bearing the wheel frame assembly and measuring the pressure and the turning torque of the wheel frame assembly on the test bed.

Description

Technical Field

[0001] This application belongs to the field of aircraft landing gear testing technology, and specifically relates to a testing device and testing method for a large landing gear main wheel turning mechanism. Background Technology

[0002] Large landing gear is typically used in large aircraft and bears heavy loads. When the landing gear turns, the torque required to control the turning is also relatively large, and many factors influence this turning torque, such as main wheel load, tire deformation, main wheel track, and the control mechanism itself. To better determine the relationship between these factors and the required control torque, a testing device for the main wheel turning mechanism of large landing gear is needed. Summary of the Invention

[0003] The purpose of this application is to provide a testing device and method for a large landing gear main wheel turning mechanism, so as to solve or alleviate at least one of the problems in the background art.

[0004] On the one hand, the technical solution of this application is: a test device for a large landing gear main wheel turning mechanism, comprising: a support frame, a loading actuator, a crossbeam, a turning loading mechanism, a wheel frame assembly, and a test bench;

[0005] The loading actuator is mounted on the support frame. One end of the loading actuator is connected to the crossbeam, and the other end is connected to the support frame. It is used to adjust the pressure of the wheel frame assembly on the test bench.

[0006] The crossbeam is pivotally connected to the support frame, with one end connected to the loading actuator and the other end equipped with one or more wheel frame assemblies;

[0007] The turning loading mechanism is mounted on the crossbeam and is used to apply a turning torque to the wheel frame assembly;

[0008] The test bench is mounted on a support frame to support the wheel frame assembly and to measure the pressure and turning torque exerted by the wheel frame assembly on the test bench.

[0009] Preferably, the support frame is a frame structure.

[0010] Preferably, the loading actuator is a hydraulic actuator cylinder.

[0011] Preferably, the crossbeam has multiple mounting holes along its length for adjusting the position of the crossbeam relative to the support frame or wheel frame assembly.

[0012] Preferably, the wheel frame assembly includes a wheel and an axle, the axle being mounted on the test bench through mounting holes on the crossbeam 30, and the spacing between two adjacent wheel frame assemblies being adjusted through mounting holes on the crossbeam.

[0013] Preferably, the distance between the wheel on the axle and the crossbeam is adjustable.

[0014] Preferably, the turning loading mechanism includes a turning actuator, a connecting rod, and a rocker arm. The turning actuator and the connecting rod are symmetrically connected to the mounting joints on both sides of the wheel axle. One end of the rocker arm is hinged to the crossbeam, the other end is hinged to the turning actuator, and the middle end is hinged to the connecting rod, thereby forming a four-bar linkage mechanism with the turning actuator, connecting rod, rocker arm, and wheel axle.

[0015] Preferably, the torque M applied to the axle by the turning actuator satisfies:

[0016] M = F zdt *L1+F zdt *L3 / L4*L2

[0017] In the formula, F zdt Output force for the turning actuator;

[0018] L1 is the force arm of the turning actuator;

[0019] L2 is the lever arm of the connecting rod;

[0020] L3 is the rocker arm torque.

[0021] L4 is the torque at the intersection of the connecting rod and the rocker arm.

[0022] Preferably, the test bench includes a bottom table, a middle table, and a top table, with a first sensor disposed between the bottom table and the middle table, and a second sensor disposed between the middle table and the top table.

[0023] Preferably, the material of the top platform is changed according to the operating environment of the aircraft landing gear.

[0024] Preferably, the first sensor and the second sensor are different sensor types.

[0025] Preferably, the first sensor is a torque sensor and the second sensor is a force sensor.

[0026] On the other hand, this application provides a method for testing using any of the above-described large landing gear main wheel steering mechanism testing devices, comprising:

[0027] S10, one or more wheel frame assemblies are mounted on the crossbeam, and a tension is applied by a loading actuator to rotate the crossbeam about the fulcrum on the support frame, thereby applying a predetermined pressure to the wheel frame assembly on the test bench;

[0028] S20, applying a turning torque to the axle of the wheel frame assembly through the turning actuator in the turning loading mechanism, and attaching strain gauges to the connecting rod of the wheel frame assembly;

[0029] S30, acquire the torque value applied by the turning actuator, the strain gauge value attached to the connecting rod, and the measurement values ​​of the first and second sensors in the test bench;

[0030] S40, the pressure of the wheel frame assembly applied by the loading actuator on the test bench and the turning torque applied by the turning actuator are checked and verified through the first sensor and / or the second sensor, and the first sensor and the second sensor form a mutual verification.

[0031] The large landing gear main wheel turning device testing device provided in this application can realize the turning torque test of multiple main wheels. The measured data is independently tested, which can better solve the problem of large load on the main wheels. The test process can realize the measurable and controllable output torque and pressure of the turning actuator, and can realize stress monitoring of the connecting rod. Through the mutual verification of the first sensor and the second sensor, the measurement results are accurate and reliable. Attached Figure Description

[0032] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0033] Figure 1 This is a schematic diagram of the test device for the large landing gear main wheel turning mechanism of this application.

[0034] Figure 2 This is a top view of the test device for the large landing gear main wheel turning mechanism of this application.

[0035] Figure 3 This is a schematic diagram of the turning loading mechanism of this application.

[0036] Figure 4 This is a schematic diagram of the test bench used in this application.

[0037] Figure 5 This is a top view of the test bench used in this application. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0039] like Figure 1 and Figure 2 As shown, the large landing gear main wheel turning mechanism testing device provided in this application includes: a support frame 10, a loading actuator 20, a crossbeam 30, a turning loading mechanism 40, a wheel frame assembly 50, and a test bench 60.

[0040] The support frame 10 is a frame structure, which is installed and fixed on the laboratory floor for bearing load.

[0041] The loading actuator 20 is vertically mounted on the support frame 10, with its upper side connected to the support frame 10 and its lower side connected to the crossbeam 30, for providing tensile load to the crossbeam 30. In a preferred embodiment of this application, the loading actuator 20 is a hydraulic actuator, thereby providing stable loading.

[0042] A crossbeam 30 is mounted on the support frame 10. Its left side is connected to the loading actuator cylinder 20, its middle part is hinged to the support frame 10, and its right side is used for mounting the wheel frame assembly 50. The crossbeam 30 has multiple mounting holes along its length for adjusting the position or distance of the crossbeam 30 relative to the support frame 10 or the wheel frame assembly 50.

[0043] The wheel frame assembly 50 includes a wheel 51 and an axle 52, with the axle 52 passing through mounting holes on the crossbeam 30 and mounted on the test bench 60. In some embodiments of this application, the number of wheel frame assemblies 50 can be two or more, and the distance between two adjacent wheel frame assemblies 50 can be adjusted via mounting holes on the crossbeam 30. Furthermore, the distance between the wheel 51 on the axle 52 and the crossbeam 30 can be adjusted; that is, the distance between the wheel 51 on both sides of the crossbeam 30 in a single wheel frame assembly 50 and the crossbeam 30 can be the same or different.

[0044] like Figure 3 As shown, the turning loading mechanism 40 includes a turning actuator 41, a connecting rod 42, and a rocker arm 43. The turning actuator 41 and connecting rod 42 are symmetrically connected to the mounting joint of the wheel axle 52. The rocker arm 3 is U-shaped, with its lower end hinged to the crossbeam 30, its upper end hinged to the turning actuator 41, and its middle end hinged to the connecting rod 42. Thus, the turning actuator 41, connecting rod 42, rocker arm 43, and wheel axle 52 form a four-bar linkage. The torque M applied to the wheel axle 52 by the turning actuator 41 satisfies:

[0045] M = F zdt *L1+F zdt *L3 / L4*L2

[0046] In the formula, F zdt Output force for the turning actuator;

[0047] L1 is the force arm of the turning actuator;

[0048] L2 is the lever arm of the connecting rod;

[0049] L3 is the rocker arm torque.

[0050] L4 is the torque at the intersection of the connecting rod and the rocker arm.

[0051] Because the lever arm L3 is greater than the lever arm L4, the torque output through the turning actuator is amplified.

[0052] like Figure 4 and Figure 5 As shown, the test bench 60 includes a bottom platform 61, a middle platform 62, and a top platform 63. A first sensor 64 is disposed between the bottom platform 61 and the middle platform 62, and a second sensor 65 is disposed between the middle platform 62 and the top platform 63. In this application, the first sensor 64 and the second sensor 65 are different sensor types.

[0053] In this application, the material of the top surface 63 can be changed according to the operating environment of the aircraft landing gear, for example, it can be set as an asphalt surface, a concrete surface, etc.

[0054] In some embodiments of this application, the first sensor 64 is a torque sensor, and the second sensor is a force-multiplying sensor. It is understood that the positions of the first sensor 64 and the second sensor 65 can be interchanged.

[0055] Based on this, this application also provides a method for testing based on the above-mentioned landing gear main wheel steering mechanism testing device, including:

[0056] S10, one or more wheel frame assemblies 50 are mounted on the crossbeam 30, and a tension is applied by the loading actuator 10 to rotate the crossbeam 30 about the fulcrum on the support frame 10, thereby applying a predetermined pressure to the test bench 60 by the wheel frame assembly 50, which can be adjusted according to the load-bearing requirements of the landing gear;

[0057] For example, in the illustrated embodiment of this application, there are two wheel frame assemblies 50 being tested, which are arranged along the length of the crossbeam 30. It is understood that there may also be three or more wheel frame assemblies 50 being tested, which will not be described in detail here.

[0058] S20, a turning torque is applied to the axle 52 of the wheel frame assembly 50 through the turning actuator 41 in the turning loading mechanism 40, and strain gauges are attached to the connecting rod 42 of the wheel frame assembly 50.

[0059] S30, acquire the torque value applied by the turning actuator 41, the strain gauge value attached to the connecting rod 42, and the measurement values ​​of the first sensor 64 and the second sensor 65 in the test bench 60;

[0060] S40, the pressure of the wheel frame assembly 60 applied by the loading actuator 10 on the test bench and the turning torque applied by the turning actuator 41 are checked and verified through the first sensor 64 and / or the second sensor 65, and the first sensor 64 and the second sensor 65 also form a mutual verification.

[0061] The large landing gear main wheel turning device testing device provided in this application can realize the turning torque test of multiple main wheels. The measured data is independently tested, which can better solve the problem of large load on the main wheels. The test process can realize the measurable and controllable output torque and pressure of the turning actuator, and can realize stress monitoring of the connecting rod. Through the mutual verification of the first sensor and the second sensor, the measurement results are accurate and reliable.

[0062] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A testing device for a large landing gear main wheel turning mechanism, characterized in that, include: Support frame, loading actuator, crossbeam, turning loading mechanism, wheel frame assembly and test bench; The loading actuator is mounted on the support frame. One end of the loading actuator is connected to the crossbeam, and the other end is connected to the support frame. It is used to adjust the pressure of the wheel frame assembly on the test bench. The crossbeam is pivotally connected to the support frame, with one end connected to a loading actuator and the other end equipped with one or more wheel frame assemblies. The crossbeam has multiple mounting holes along its length for adjusting the position of the crossbeam relative to the support frame or wheel frame assembly. The wheel frame assembly includes a wheel and an axle. The axle passes through the mounting holes on the crossbeam and is mounted on the test bench. The distance between two adjacent wheel frame assemblies is adjusted through the mounting holes on the crossbeam. The turning loading mechanism is mounted on the crossbeam and is used to apply turning torque to the wheel frame assembly. The turning loading mechanism includes a turning actuator, a connecting rod, and a rocker arm. The turning actuator and the connecting rod are symmetrically connected to the mounting joints on both sides of the wheel axle. One end of the rocker arm is hinged to the crossbeam, the other end is hinged to the turning actuator, and the middle end is hinged to the connecting rod, so that the turning actuator, connecting rod, rocker arm, and wheel axle form a four-bar linkage. The test bench is mounted on a support frame to support the wheel frame assembly and to measure the pressure and turning torque of the wheel frame assembly on the test bench. Wherein, the torque M applied to the wheel axle by the turning actuator satisfies: M=F zdt *L1+F zdt *L3 / L4*L2 In the formula, F zdt Output force for the turning actuator; L1 is the force arm of the turning actuator; L2 is the lever arm of the connecting rod; L3 is the rocker arm torque. L4 is the torque at the intersection of the connecting rod and the rocker arm.

2. The testing device for the large landing gear main wheel turning mechanism as described in claim 1, characterized in that, The support frame is a frame structure.

3. The testing device for the large landing gear main wheel turning mechanism as described in claim 1, characterized in that, The loading actuator is a hydraulic actuator cylinder.

4. The testing device for the large landing gear main wheel turning mechanism as described in claim 1, characterized in that, The distance between the wheel on the axle and the crossbeam can be adjusted.

5. The testing device for the large landing gear main wheel turning mechanism as described in claim 1, characterized in that, The test bench includes a bottom table, a middle table, and a top table. A first sensor is installed between the bottom table and the middle table, and a second sensor is installed between the middle table and the top table.

6. The testing device for the large landing gear main wheel turning mechanism as described in claim 5, characterized in that, The material of the top platform is changed according to the operating environment of the aircraft landing gear.

7. The testing device for the large landing gear main wheel turning mechanism as described in claim 5, characterized in that, The first sensor and the second sensor are different sensor types.

8. The testing device for the large landing gear main wheel turning mechanism as described in claim 7, characterized in that, The first sensor is a torque sensor, and the second sensor is a force sensor.

9. A method for testing a large landing gear main wheel turning mechanism using the testing device as described in any one of claims 1 to 8, characterized in that, include: S10, one or more wheel frame assemblies are mounted on the crossbeam, and a tension is applied by a loading actuator to rotate the crossbeam about the fulcrum on the support frame, thereby applying a predetermined pressure to the wheel frame assembly on the test bench; S20, applying a turning torque to the axle of the wheel frame assembly through the turning actuator in the turning loading mechanism, and attaching strain gauges to the connecting rod of the wheel frame assembly; S30, obtain the torque value applied by the turning actuator, the strain gauge values ​​attached to the connecting rod, and The measured values ​​of the first and second sensors in the test bench; S40, the pressure of the wheel frame assembly applied by the loading actuator on the test bench and the turning torque applied by the turning actuator are checked and verified through the first sensor and / or the second sensor, and the first sensor and the second sensor form a mutual verification.

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